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Home/Contractors/Busek CO., INC./contracts

Federal Contractor Profile

Busek CO., INC.

$67M obligated·104 awards·2 agencies·4 NAICS
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Federal Contracts

Showing award actions 101–124 of 124 funded award actions, most recent first.

Contracts with positive obligations
104
Funded award actions shown
124
Obligations shown
$67M
Awarding agencies
2

This table shows award actions with a positive obligation. Zero-dollar and negative-dollar actions, such as administrative changes and deobligations, are not displayed. Multiple award actions may belong to the same contract.

Award data as of September 9, 2026. Source: USAspending federal award records.

DateAgencyPIIDNAICSDescriptionAmount
Mar 9, 2017Department of DefenseMISSILE DEFENSE AGENCY (MDA)HQ014717C7103541712IGF::OT::IGF STTR PHASE II RESEARCH&DEV$996K
Mar 8, 2017Department of DefenseNAVAIR WARFARE CTR AIRCRAFT DIVN6833517C0265541712IGF::OT::IGF PHASE I TOPIC #N163-139$80K
Dec 20, 2016Department of DefenseFA9300 AFTC PZRFA930014C3000541712IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT$2K
Dec 7, 2016Department of DefenseFA9300 AFTC PZRFA930014C3000541712IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT$100K
Oct 27, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX14CC24C541712IGF::OT::IGF IN PHASE I BUSEK MATURED THE DESIGN OF AN EXISTING 15-KW LABORATORY THRUSTER. MAGNETIC MODELING WAS PERFORMED TO GENERATE A CIRCUIT INCORPORATING MAGNETIC SHIELDING. EROSION MODELING PREDICTS EXTREMELY LONG LIFETIME AND HIGH THROUGHPUT. A DETAILED MECHANICAL DESIGN OF THE THRUSTER RESULTED IN AN OVERALL ASSEMBLY WITH SPECIFIC MASS<3KG/KW. MODAL, DYNAMIC AND THERMAL ANALYSES WERE PERFORMED TO CALCULATE RESONANCE FREQUENCIES, MODE SHAPES, STRESS AND FATIGUE VALUES AND TEMPERATURE LIMITS. EXPERIMENTS USING THE EXISTING LABORATORY THRUSTER EVALUATED A MODIFIED ANODE/GAS DISTRIBUTOR AND A B-FIELD DISTRIBUTION REPRESENTATIVE OF THE PROPOSED MAGNETIC SHIELDED CONFIGURATION. PERFORMANCE RESULTS SUGGEST SIMILAR EFFICIENCY AND PERFORMANCE AS THE BASELINE THRUSTER. VISUAL OBSERVATION OF THE PLUME ILLUSTRATED THE CHARACTERISTICS OF MAGNETIC SHIELDING WERE ACHIEVED. IN PHASE II BUSEK WILL COMPLETE THE DETAILED DESIGN OF THE THRUSTER AND A CENTER MOUNTED HOLLOW CATHODE. A PROTOTYPE UNIT WILL BE FABRICATED AND PERFORMANCE TESTED INCLUDED LIMITED DURATION TESTING AT BUSEK. DEPENDING ON FACILITY AVAILABILITY THE THRUSTER WILL INDEPENDENTLY TESTED AT GRC. BUSEK WILL HOLD A MRR AND CDR THEN FABRICATE, ASSEMBLE, AND FULLY TEST A QUALIFICATION MODEL THRUSTER/CATHODE TO RAISE THE MATURITY TO TRL 6. THE THRUSTER WILL BE DELIVERED TO NASA FOR EXTENDED DURATION TESTING TO COMPLETE THE QUALIFICATION.$125K
Oct 25, 2016National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTERNNC15CA06C541712THE DEVELOPMENT OF CRITICAL COMPONENTS FOR 600W IODINE HALL PROPULSION SYSTEM IS A SBIR PHASE III FOLLOW-ON TO WORK COMPLETED UNDER SBIR PHASE I CONTRACT NNX12CD99P AND SBIR PHASE II CONTRACT NNX13CC82C. IGF::OT::IGF$55K
Sep 7, 2016Department of DefenseNAVAL INFORMATION WARFARE SYSTEMSN0003915C0228541712IGF::OT::IGF, 6U CUBESAT RADAR ALTIMETER STUDY$748K
Jul 28, 2016Department of DefenseFA9300 AFTC PZRFA930014C3000541712IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT$45K
Jul 27, 2016Department of DefenseFA9300 AFTC PZRFA930015C2000541712IGF::OT::IGF SBIR PHASE II - LOW MASS LOW SPECIFIC POWER HALL EFFECT THRUSTER$187K
Jul 25, 2016Department of DefenseFA9300 AFTC PZRFA930014C2500541712IGF::OT::IGF SMALL BUSINESS TECHNOLOGY TRANSFER (STTR) PHASE II - ULTRA HIGH-DENSITY ION PROPULSION FROM IONIC LIQUIDS$100K
Jun 27, 2016Department of DefenseFA9453 AFRL RVKFA945316M0523541712IGF::OT::IGF NOVEL IONIC LIQUIDS FOR REVERSIBLE ELECTROPLATING$150K
Jun 10, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CK11P541712IGF::OT::IGF BUSEK, IN PARTNERSHIP WITH ARIZONA STATE UNIVERSITY (ASU), PROPOSES TO DEVELOP A ROBOTIC RESOURCE PROSPECTING MISSION TO A NEAR-EARTH ASTEROID USING A 6U CUBESAT, NICKNAMED "ASTROCUBE". THIS AMBITIOUS MISSION IS ENABLED BY BUSEK'S IODINE-FUELED BIT-3 RF ION PROPULSION SYSTEM THAT CAN DELIVER ~1MN OF THRUST AND ~2200SEC OF TOTAL ISP WITH 65W NOMINAL INPUT POWER. WITH 1.6KG OF SOLID IODINE PROPELLANT ONBOARD, THE BIT-3 THRUSTER WILL PROVIDE ASTROCUBE APPROXIMATELY 3.1KM/S OF DELTA-V MANEUVERABILITY TO RENDEZVOUS WITH THE TARGET, ASTEROID 2001 GP2, DURING ITS NEXT CLOSEST EARTH APPROACH IN OCTOBER 2020. THE 6U CUBESAT PLATFORM IS CHOSEN DUE TO ITS LOW COST AND EASE OF ACCESS TO RIDE-SHARE OPPORTUNITY ON GEO-BOUND UPPER STAGES, AS WELL AS ON THE UPCOMING NASA SLS DEMONSTRATION MISSIONS. THE ASTROCUBE MISSION WILL LEVERAGE A UNIQUE DEEP-SPACE 6U CUBESAT BUS WITH ION PROPULSION, CURRENTLY BEING CO-DEVELOPED BY BUSEK AND MOREHEAD STATE UNIVERSITY (MSU) UNDER NASA'S LUNAR ICECUBE FLIGHT PROGRAM. THE PROPOSED MISSION WILL ENCOMPASS SEVERAL TECHNOLOGY INNOVATIONS, INCLUDING COMPACT SCIENCE INSTRUMENTS AND AUTONOMOUS CONOPS, WHICH ARE THE FOCUS OF THIS PHASE I DEVELOPMENT. A RAD-TOLERANT, 1/4U SIZED CAMERA-LIDAR DEVICE WILL GIVE ASTROCUBE "EYES" TO SURVEY THE ASTEROID AND HELP WITH PROXIMITY NAVIGATION. DUE TO THE ASTEROID'S WEAK GRAVITATIONAL FIELD, THE SPACECRAFT WILL BE REQUIRED TO USE REAL-TIME DEPTH IMAGE PROCESSING AND ITS ION THRUSTER TO NAVIGATE AROUND THE ASTEROID DURING FINAL APPROACH TO A LOW STATIONARY ALTITUDE. ONCE SUCH CLOSE PROXIMITY IS REACHED, A 1U SIZED NEUTRON SPECTROMETER WILL BE ACTIVATED TO CHARACTERIZE THE ABUNDANCE OF HYDROGEN, WHICH WOULD INDICATE PRESENCE OF WATER ICE, BY DETECTING SLOW-MOVING NEUTRONS AS THEY SCATTER OFF THE ASTEROID'S REGOLITH FROM THE BOMBARDMENT OF COSMIC RAYS.$125K
Jun 10, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CC54P541712IGF::OT::IGF BUSEK PROPOSES TO DEVELOP A COMPACT ELECTROSPRAY PROPULSION SYSTEM WITH UNPRECEDENTED CAPABILITY. THE<2U SYSTEM WILL PROVIDE 6U CUBESATS WITH 1000M/S OF DELTAV AT 1.2MN THRUST AND>1500S ISP WHILE REQUIRING LESS THAN 45W OF POWER. COMPARED WITH EXISTING STATE-OF-THE-ART CUBESAT THRUSTERS, THE SYSTEM WILL PROVIDE MORE THRUST THAN AVAILABLE GRIDDED ION ENGINES AT LOWER POWER AND WITHOUT GREATLY PENALIZING ISP. BUSEK WILL DEVELOP THE THRUSTER THROUGH NEW INNOVATIONS MERGED WITH EXISTING, FLIGHTQUALIFIED ELECTROSPRAY THRUSTER HERITAGE. THE EXTREMELY LOW FLOW RATES OF HIGH ISP ELECTROSPRAY THRUSTERS PERMITS PASSIVE FEEDING, WHERE PRESSURE VESSELS, REGULATORS AND THEIR ASSOCIATED ELECTRONICS ARE ELIMINATED IN FAVOR OF A NATURAL FLOW REGULATION; FREEING UP VALUABLE VOLUME BUDGET FOR ADDITIONAL PROPELLANT OR PAYLOAD. HOWEVER, PASSIVE ELECTROSPRAY THRUSTERS IN GENERAL SUFFER FROM FLOW CONTROL AMBIGUITIES, LEADING TO IRRECOVERABLE FAILURES DUE TO THE CONDUCTIVE PROPELLANT DEGRADING OR SHORTING ELECTRICAL ISOLATORS. BUSEK WILL INTEGRATE NEW INNOVATIONS THAT OVERCOME THESE ISSUES INTO A SYSTEMATIC DEVELOPMENT METHODOLOGY, LEADING TO THE MOST ROBUST PASSIVELY-FED ELECTROSPRAY THRUSTER TO DATE. THE SYSTEM WILL BE CAPABLE OF MORE 0.7KG OF PROPELLANT THROUGHPUT (~1000M/S DELTAV FOR A 6U CUBESAT) AND BE FULLY SCALABLE TO HIGHER CAPACITY.IN PHASE I BUSEK WILL DEVELOP A THRUSTER HEAD THAT PROVIDES>300MICRON OF THRUST AND INCLUDES A NEVER-SATURATED POROUS RESERVOIR. THE RESTORATIVE CAPILLARY FORCE OF THIS RESERVOIR WILL PREVENT LIQUID SEEPAGE AND MAINTAIN CONSISTENT PERFORMANCE. AN ANNULAR GEOMETRY WILL CIRCUMVENT PROPELLANT AND SURFACE DEGRADATION DUE TO EDGE EFFECTS. IN PARALLEL, A METHOD FOR TRANSFERRING IL FROM HIGH OPEN VOLUME STORAGE TANKS TO THE INTERMEDIATE POROUS RESERVOIR WILL BE DEMONSTRATED. FINALLY, THE COMPLETE 1.2MN THRUSTER, COMPRISING AN ARRAY OF 4 THRUSTER HEADS WILL BE DESIGNED. PHASE II, WILL VALIDATE THIS SYSTEM AND CULMINATE WITH DELIVERING AN ENGINEERING MODEL$125K
Jun 5, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CJ33P541712IGF::OT::IGF THE CONVERSION OF HEAT TO POWER HAS PROVEN TO BE VITAL IN FLIGHT MISSIONS WHERE SOLAR POWER GENERATION IS NOT AN OPTION. RADIOISOTOPE THERMOELECTRIC GENERATORS THAT CONVERTED HEAT PRODUCED BY A DECAYING NUCLEAR SOURCE TO POWER HAVE BEEN USED ON MISSIONS SUCH AS CASSINI, NEW HORIZONS, GALILEO, ULYSSES AND THE MARS SCIENCE LABORATORY. ALTHOUGH NEVER FLOWN BY THE UNITED STATES, THERMIONIC CONVERTERS HAVE ALSO BEEN INVESTIGATED FOR SPACE APPLICATIONS. THEIR IMPROVED EFFICIENCY OVER THERMOELECTRIC GENERATORS MAKES THEM AN ATTRACTIVE OPTION, BUT THE HIGH OPERATING TEMPERATURES REQUIRED HAVE THUS FAR BEEN A SIGNIFICANT OBSTACLE TO THEIR USE. THERMIONIC GENERATORS CONVERT HEAT ENERGY DIRECTLY INTO ELECTRICAL POWER. AN EMITTER ELECTRODE ON A HEAT SOURCE EMITS ELECTRONS ACROSS A VACUUM GAP TO A COLD ELECTRODE. THE GENERATED CURRENT IS PUMPED THROUGH A LOAD WHERE IT CAN DO USEFUL WORK BEFORE IT IS RETURNED TO THE EMITTER. THERMIONIC GENERATORS DO NOT USE ANY MOVING PARTS OR WORKING FLUID, WHICH RESULTS IN HIGHLY RELIABLE DEVICES THAT DO NOT NEED FREQUENT MAINTENANCE. UNLIKE THERMOELECTRIC GENERATORS, WHICH HAVE EXHIBITED EFFICIENCIES ONLY UP TO ABOUT 8%, STATE-OF-THE-ART THERMIONIC GENERATORS OPERATE WITH EFFICIENCIES APPROACHING 20%. THIS PROPOSAL SEEKS TO STUDY THE USE OF THE NANOMATERIAL C12A7 ELECTRIDE AS AN ELECTRODE MATERIAL. C12A7 ELECTRIDE HAS BEEN SHOWN TO EMIT STABLY AT TEMPERATURES IN EXCESS OF 1600 DEGREES C AND HAS A MEASURED WORK FUNCTION BETWEEN 0.8-2.1 EV. DUE TO ITS LOW WORK FUNCTION, C12A7 ELECTRIDE HAS THE POTENTIAL TO GREATLY IMPROVE THE EFFICIENCY OF THE STATE-OF-THE-ART IN THERMIONIC ENERGY CONVERSION AS WELL AS ENABLE DEVICE OPERATION AT MUCH LOWER TEMPERATURES THAN IS CURRENTLY POSSIBLE. BUSEK PREVIOUSLY HAS INVESTIGATED C12A7 ELECTRIDE IN THERMIONIC EMISSION CONFIGURATIONS FOR SPACE PROPULSION HOLLOW CATHODE APPLICATIONS. IN THE PROPOSED WORK, BUSEK WILL EVALUATE THE POTENTIAL BENEFITS OF A C12A7 ELECTRIDE THERMIONIC CONVERTER ELECTRODE.$125K
Jun 1, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CC02C541712IGF::OT::IGF AS PART OF A NASA GAME CHANGING TECHNOLOGIES PROGRAM, BUSEK DEVELOPED A FULLY INTEGRATED PROTOTYPE 100UN-CLASS SYSTEM (BET-100UN) SUITABLE FOR INTEGRATION INTO CUBESAT PLATFORMS. THIS STATEMENT OF WORK OUTLINES THE EFFORT TO FLIGHT-QUALIFY THE ELECTROSPRAY SYSTEM DEVELOPED AS PART OF THE MICROFLUIDIC ELECTROSPRAY PROPULSION (MEP) PHASE I PROGRAM. THE FINAL INTEGRATED UNITS DELIVERED AS PART OF THE PHASE I WERE INTENDED TO BE VIABLE FOR LOW EARTH ORBIT (LEO) DEMONSTRATION AFTER COMPLETION OF A QUALIFICATION EFFORT. THE WORK DESCRIBED HEREIN IS INTENDED TO: PERFORM ADDITIONAL ANALYSIS AND TESTING TO FURTHER CHARACTERIZE THE PHASE I DELIVERABLE DESIGN, CONDUCT A QUALIFICATION PROGRAM, FABRICATE FLIGHT HARDWARE, SUPPORT PROPULSION SYSTEM INTEGRATION INTO THE SPACECRAFT, AND SUPPORT FLIGHT OPERATIONS. THE FLIGHT UNITS ARE INTENDED FOR INTEGRATION INTO A 6U CUBESAT AND LEO DEMONSTRATION AS PART OF THE NASA PATHFINDER TECHNOLOGY DEMONSTRATOR PROJECT, SPONSORED BY THE SMALL SPACECRAFT TECHNOLOGY PROGRAM (SSTP). THE INTEGRATED ELECTROSPRAY THRUSTER SYSTEM CONSISTS OF A TWO-BOARD ELECTRICAL STACK, WITH EXTERNAL DIMENSIONS OF 9.5CM X 9.5CM X 3.3CM, EQUIVALENT TO 1/3U IN A CUBESAT FROM FACTOR. THE FIRST 9.5CM X 9.5CM BOARD HOUSES THE ENTIRETY OF THE ELECTRONICS; A POWER PROCESSING UNIT (PPU), AND THE DIGITAL CONTROL INTERFACE UNIT (DCIU) LOCATED ON A SMALL MEZZANINE BOARD. THE SECOND 9.5CM X 9.5CM BOARD HOUSES THE 100?N ELECTROSPRAY THRUSTER, AS WELL AS A CARBON NANOTUBE FIELD EMISSION CATHODE (CNTFEC) USED TO NEUTRALIZE THE EMITTED ELECTROSPRAY BEAM.$158K
May 13, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CM06C541712IGF::OT::IGF BUSEK IS DEVELOPING AN ADVANCED IODINE FEED SYSTEM FOR HALL EFFECT THRUSTERS (HETS), ION ENGINES, CATHODES, AND OTHER PLASMA GENERATORS. THE FEED SYSTEM FEATURES AN INNOVATIVE PIEZO DRIVEN VALVE THAT SAVES VOLUME, MASS, COST, AND ENERGY WITH RESPECT TO STATE OF THE ART ALTERNATIVES. THE FEED SYSTEM ALSO FEATURES A LOW MASS PLASTIC PROPELLANT TANK THAT MAY BE MANUFACTURED THROUGH ADDITIVE PROCESSES. THIS ALLOWS LOW COST, COMPLEX SHAPES THAT CAN MAXIMIZE THE USE OF AVAILABLE SPACE INSIDE VOLUME-RESTRICTED SPACECRAFT. THE FEED SYSTEM WILL BE ESPECIALLY ATTRACTIVE FOR SMALL SPACECRAFT AND CUBESATS. IODINE STORES AS A SOLID AND SUBLIMATES AT MODEST TEMPERATURES AS THE MOLECULE I2, WHICH ALLOWS MANY BENEFITS WITH RESPECT TO TRADITIONAL HALL EFFECT THRUSTER FUELS SUCH AS XENON AND KRYPTON. THESE ADVANTAGES INCLUDE HIGHER STORAGE DENSITY, LOWER STORAGE PRESSURE, THE ABILITY TO TEST HIGH POWER SYSTEMS AT SPACERELEVANT CONDITIONS IN MODEST FACILITIES, THE CAPABILITY TO STORE PROPELLANT IN SPACE WITHOUT ACTIVE REGULATION, AND THE CAPACITY TO TRANSFER PROPELLANT AT LOW-PRESSURE CONDITIONS IN SPACE. IN A SPACE-LIMITED SPACECRAFT, USING IODINE INSTEAD OF STATE OF THE ART XENON COULD INCREASE AVAILABLE DELTA-V BY A FACTOR OF THREE (3) OR MORE. IN PHASE I, BUSEK DEVELOPED A FEED SYSTEM FEATURING THE ADVANCED COMPONENTS, WHICH WAS INTEGRATED INTO THE ISAT SPACECRAFT FORM FACTOR. THE SYSTEM WAS THEN TESTED WITH AN IODINE COMPATIBLE HALL EFFECT THRUSTER IN RELEVANT SPACE CONDITIONS. IN PHASE II, AN IMPROVED FEED SYSTEM WILL BE DESIGNED, BUILT AND TESTED. MAJOR PHASE II TECHNICAL OBJECTIVES INCLUDE DEVELOPING AN ENGINEERING MODEL IODINE RESISTANT, PIEZO DRIVEN FLOW CONTROL VALVE, FINALIZING THE FEED SYSTEM CONTROL ARCHITECTURE, IDENTIFYING AND EVALUATE COMMERCIAL COMPONENTS TO FILL OUT THE SYSTEM, AND BUILDING AND CHARACTERIZING THE SYSTEM. AT THE CONCLUSION OF THE PHASE II EFFORT, ENGINEERING MODEL VALVES WILL BE DELIVERED TO NASA FOR FURTHER CHARACTERIZATION.$750K
May 4, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CJ05C541712IGF::OT::IGF BUSEK CO. INC. PROPOSES TO ADVANCE THE MATURITY OF AN INNOVATIVE SPACECRAFT ON UMBILICAL LINE (SOUL) SYSTEM SUITABLE FOR A WIDE VARIETY OF APPLICATIONS OF INTEREST TO NASA, DOD AND COMMERCIAL MISSIONS. SOUL IS A SMALL (<10KG) ROBOTIC, SELF-PROPELLED, SELF-NAVIGATING, AUTONOMOUS VEHICLE EQUIPPED WITH A TOOL (E.G. GRIPPER, LIGHT, CAMERA ETC.). THE SOUL VEHICLE/ROBOT IS ATTACHED VIA THE UMBILICAL LINE TO A LARGER HOST SPACECRAFT THAT STOWS IT IN A MARSUPIAL-LIKE MANNER AND COMMUNICATES WITH GROUND. THE UMBILICAL DELIVERS POWER AND COMMANDS TO SOUL FROM THE HOST SPACECRAFT. CONCEPTUALLY, THE SOUL IS A TOOL ON THE END OF TENS OF METERS LONG ROBOTIC ARM WITH INFINITE DEGREES OF FREEDOM (FLEXIBLE UMBILICAL) THAT CAN ACCESS LOCATIONS UNREACHABLE BY CONVENTIONAL ROBOTIC ARMS. THE INITIAL PURPOSE OF THE USAF AND NAVY FUNDED SOUL DEVELOPMENT WAS REMOVAL OF LARGE SPACE DEBRIS (1000KG CLASS). UNDER THIS PROGRAM, THE DEVELOPMENT OF THE SOUL VEHICLE WAS EXTREMELY SUCCESSFUL. THE SOUL, TESTED ON A AIR TABLE, AUTONOMOUSLY RECOGNIZED SIMULATED DEBRIS, ESTIMATED ITS POSE RELATIVE TO THE TARGET (FUSING VISIBLE, IR IMAGES AND IMU INFORMATION), PLANNED A PATH TO THE DEBRIS AND EXECUTED THE PATH AND THE TOUCHED THE TARGET WITH MINIMAL MOMENTUM TRANSFER. IN PHASE 1 OF THE PRESENT PROGRAM, BUSEK DESIGNED, BUILD AND TESTED A WINCH THAT IS THE KEY PART OF THE SOUL DEPLOYMENT AND RETRIEVAL SYSTEM, PANNING OUT OR REELING IN THE UMBILICAL LINE. IN THE PROPOSED PHASE 2 EFFORT BUSEK WILL BUILD THE ENTIRE SOUL SYSTEM CONSISTING OF THE SOUL VEHICLE, UMBILICAL, THE DEPLOYMENT/RETRIEVAL SYSTEM AND THE COMMAND MODULE. THE ENTIRE SYSTEM WILL BE HOUSED FOR LAUNCH IN A 6U CUBESAT DEPLOYER WHICH WILL ALSO STOW SOUL WHEN INACTIVE. DEMONSTRATION OF THE INTEGRATED SYSTEM INCLUDING THE 6U DEPLOYER WILL BE PERFORMED ON THE AIR TABLE. THE ULTIMATE GOAL IS TO MAKE A FLIGHT WORTHY SYSTEM AND DEMONSTRATE IT ON THE ISS. FLIGHT READINESS WILL BE ACHIEVED BY QUALIFYING PROGRAM ON THE PHASE 2 HARDWARE.$750K
Mar 29, 2016Department of DefenseFA9300 AFTC PZRFA930012C3000541712IGF::OT::IGF SMALL BUSINESS INNOVATIVE RESEARCH (SBIR) PHASE III - SPACE PLASMA CHARACTERIZATION SOURCE (SPCS)$50K
Mar 2, 2016Department of DefenseW6QK ACC-APGW91CRB14C0049541712IGF::OT::IGF TECHNICAL SUPPORT SERVICES$500K
Jan 22, 2016National Aeronautics and Space AdministrationNASA SHARED SERVICES CENTERNNX16CC02C541712IGF::OT::IGF AS PART OF A NASA GAME CHANGING TECHNOLOGIES PROGRAM, BUSEK DEVELOPED A FULLY INTEGRATED PROTOTYPE 100UN-CLASS SYSTEM (BET-100UN) SUITABLE FOR INTEGRATION INTO CUBESAT PLATFORMS. THIS STATEMENT OF WORK OUTLINES THE EFFORT TO FLIGHT-QUALIFY THE ELECTROSPRAY SYSTEM DEVELOPED AS PART OF THE MICROFLUIDIC ELECTROSPRAY PROPULSION (MEP) PHASE I PROGRAM. THE FINAL INTEGRATED UNITS DELIVERED AS PART OF THE PHASE I WERE INTENDED TO BE VIABLE FOR LOW EARTH ORBIT (LEO) DEMONSTRATION AFTER COMPLETION OF A QUALIFICATION EFFORT. THE WORK DESCRIBED HEREIN IS INTENDED TO: PERFORM ADDITIONAL ANALYSIS AND TESTING TO FURTHER CHARACTERIZE THE PHASE I DELIVERABLE DESIGN, CONDUCT A QUALIFICATION PROGRAM, FABRICATE FLIGHT HARDWARE, SUPPORT PROPULSION SYSTEM INTEGRATION INTO THE SPACECRAFT, AND SUPPORT FLIGHT OPERATIONS. THE FLIGHT UNITS ARE INTENDED FOR INTEGRATION INTO A 6U CUBESAT AND LEO DEMONSTRATION AS PART OF THE NASA PATHFINDER TECHNOLOGY DEMONSTRATOR PROJECT, SPONSORED BY THE SMALL SPACECRAFT TECHNOLOGY PROGRAM (SSTP). THE INTEGRATED ELECTROSPRAY THRUSTER SYSTEM CONSISTS OF A TWO-BOARD ELECTRICAL STACK, WITH EXTERNAL DIMENSIONS OF 9.5CM X 9.5CM X 3.3CM, EQUIVALENT TO 1/3U IN A CUBESAT FROM FACTOR. THE FIRST 9.5CM X 9.5CM BOARD HOUSES THE ENTIRETY OF THE ELECTRONICS; A POWER PROCESSING UNIT (PPU), AND THE DIGITAL CONTROL INTERFACE UNIT (DCIU) LOCATED ON A SMALL MEZZANINE BOARD. THE SECOND 9.5CM X 9.5CM BOARD HOUSES THE 100?N ELECTROSPRAY THRUSTER, AS WELL AS A CARBON NANOTUBE FIELD EMISSION CATHODE (CNTFEC) USED TO NEUTRALIZE THE EMITTED ELECTROSPRAY BEAM.$1.6M
Dec 30, 2015Department of DefenseFA8601 AFLCMC PZIOFA860116P0054334519ADVANCED MICRO PULSED PLASMA THRUSTER$160K
Dec 30, 2015Department of DefenseFA8601 AFLCMC PZIOFA860116P0046334519PSEUDO LINEAR HALL THRUSTER$100K
Nov 25, 2015Department of DefenseFA9300 AFTC PZRFA930014C3000541712IGF::OT::IGF SMALL BUSINESS INNOVATION RESEARCH PHASE III, ADVANCED MONOPROPELLANT APPLICATION FOR CUBESAT$78K
Nov 20, 2015National Aeronautics and Space AdministrationGLENN RESEARCH CENTERNNC15CA06C541712THE DEVELOPMENT OF CRITICAL COMPONENTS FOR 600W IODINE HALL PROPULSION SYSTEM IS A SBIR PHASE III FOLLOW-ON TO WORK COMPLETED UNDER SBIR PHASE I CONTRACT NNX12CD99P AND SBIR PHASE II CONTRACT NNX13CC82C. IGF::OT::IGF$260K

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